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Incompressible potential flow past ‘not-so-slender’ bodies of revolution at an angle of attack

Published online by Cambridge University Press:  29 March 2006

P. Sivakrishna Prasad  and
N. R. Subramanian
P. Sivakrishna Prasad
Affiliation:
Department of Aeronautical Engineering, Indian Institute of Technology, Madras 600036
N. R. Subramanian
Affiliation:
Department of Aeronautical Engineering, Indian Institute of Technology, Madras 600036
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Abstract

Using the method of matched asymptotic expansions, an expansion of the velocity potential for steady incompressible flow has been obtained to order ε4 for slender bodies of revolution at an angle of attack by representing the potential due to the body as a superposition of potentials of sources and doublets distributed along a segment of the axis inside the body excluding an interval near each end of the body. Also, expansions of the coefficients of longitudinal virtual mass and lateral virtual mass have been found. The pressure distributions over an ellipsoid of revolution of thickness ratio ε = 0·3 at zero angle of attack and at an angle of attack of 3° obtained by the present method are compared with results obtained from the exact theory and that of Van Dyke. The virtual-mass coefficients are also compared with those obtained from the exact theory and are found to be in good agreement up to ε = 0·3.

Type
Research Article
Information
Journal of Fluid Mechanics , Volume 70 , Issue 4 , 26 August 1975 , pp. 651 - 661
Copyright
© 1975 Cambridge University Press

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References

Ashley, H. & Landahl, M. T. 1965 Aerodynamics of Wings and Bodies. Addison-Wesley.
Broderick, J. B. 1949 Supersonic flow round pointed bodies of revolution. Quart. J. Mech. Appl. Math. 2, 98–120.Google Scholar
Cole, J. D. 1968 Perturbation Methods in Applied Mathematics, pp. 182–193. Blaisdell.
Handelsman, R. A. & Keller, J. B. 1967 Axially symmetric potential flow around a slender body. J. Fluid Mech. 28, 131–147.Google Scholar
Lighthill, M. J. 1948 Supersonic flow past pointed bodies of revolution at yaw. Quart. J. Mech. Appl. Math. 1, 77–89.Google Scholar
Matthews, C. W. 1952 A comparison of the experimental subsonic pressure distributions about several bodies of revolution with pressure distributions computed by means of the linearized theory. N.A.C.A. Tech. Note, no. 2519.Google Scholar
Munk, M. M. 1934 Fluid Mechanics, Part 2. Aerodynamic Theory, vol. 1 (ed. Durand). Dover.
Thwaites, B. 1960 Incompressible Aerodynamics, p. 401. Oxford University Press.
Van Dyke, M. D. 1951 First and second order theory of supersonic flow past bodies of revolution. J. Aero. Sci. 18, 161–178.Google Scholar
Van Dyke, M. D. 1959 Second order slender body theory-axisymmetric flow. N.A.S.A. Tech. Rep. R-47.Google Scholar
Wang, K. C. 1967 A new approach to ‘not-so-slender' wing theory. Res. Inst. Adv. Studies Tech. Rep. no. 67–10.Google Scholar